WO2006108749A1

WO2006108749A1 - Component with film cooling holes

Info

Publication number: WO2006108749A1
Application number: PCT/EP2006/060794
Authority: WO
Inventors: Thomas Beck; Silke Settegast
Original assignee: Siemens Aktiengesellschaft
Priority date: 2005-04-12
Filing date: 2006-03-16
Publication date: 2006-10-19
Also published as: US20110300000A1; EP1712739A1; ATE493565T1; EP2428646B1; KR20070120187A; KR100933095B1; EP2428646A1; US8292584B2; US20090067998A1; CN100582439C; CN101120156A; US8157526B2; EP2292898A1; EP1869290A1; EP1869290B1; DE502006008605D1

Abstract

Conventionally coated components with film cooling holes are known, comprising a diffuser, extending through the layers into the substrate. According to the invention, the component is embodied such that the whole diffuser (13) is largely arranged in the layer (7, 10).

Description

Component with film cooling hole

The invention relates to a component with a film cooling hole GE measure the preamble of claim 1.

Components for high temperature applications consist of a superalloy with additional protection against oxidation, corrosion and high temperatures. For this purpose, the substrate of the component to a corrosion protection layer on which at ^¬ play as yet an outer ceramic thermal barrier layer is placed on ^¬.

For additional cooling, through holes are also introduced into the substrate and the layers, from which a cooling medium emerges on the outer surface and contributes to film cooling. In this case, the film cooling hole is widened in the vicinity of the outer surface to a so-called diffuser. In the re-manufacturing a component with a film cooling hole, problems arise because the diffuser is introduced through both the layers and is mostly in the substrate ^¬. During refurbishment, the refurbishing of components, the problem is that the through hole is already there and coating the substrate again ^¬ the need, so then must also be removed from the diffuser area in the through hole coating material.

US Pat. No. 4,743,462 discloses a method for closing a film cooling hole in which a plug consisting of a pin and a spherical head is inserted into the film cooling hole. In this case, a bell-shaped depression is achieved within ^¬ half of the coating. However, the depression does not serve as a diffuser because it is symmetrical. In addition, the action of the head is that the material of the head evaporates during the coating. Thus, accurate, reproducible wells can not be made for a variety of film cooling holes. A similar symmetrical broadening of a film cooling hole is disclosed in FIG. 3 of US Pat. No. 5,573,474.

EP 1 350 860 A1 discloses a method for masking a film cooling hole. The material of the masking agent is chosen so that no coating material is deposited there during a subsequent coating. In this case, no precise, reproducible form of depressions within a layer can be produced. In addition, no diffuser is described here.

EP 1 091 090 A2 discloses a film cooling hole in which a groove is made in the layer so that the groove runs along a plurality of film cooling holes. Neither the film cooling holes nor the groove have a diffuser area.

US Pat. No. 5,941,686 discloses a layer system in which the substrate is processed. A diffuser area is not disclosed.

EP 1 076 107 A1 discloses a method for masking film cooling holes in which a plug is produced in each case in the film cooling hole which protrudes from the hole. For this purpose, in a first step, air is blown through the film cooling hole and a coating is applied, in which case a precursor for the plug to be produced is introduced into the film cooling hole and into the coating. The part of the plug disposed in ^¬ nerhalb the temporary layer, in its shape determined by how much a medium is blown through the film cooling hole and how is the coating of the temporary layer. Thus, the shape of the part of the plug which protrudes from the hole is not reproducible.

It is therefore an object of the invention to overcome this problem. The object is achieved by a component according to claim 1.

In the dependent claims further advantageous measures are listed, which can be connected in any manner in an advantageous manner.

Show it

Figures 1 to 6 show exemplary embodiments of a erfindungsge ^¬ MAESSEN component with a film cooling hole, Figure 7, Figure 8 shows a plan view of a erfindungsge ^¬ mäßes film cooling hole,

Figure 9 to 13 embodiments of a film cooling hole, Figure 14 illustrates the disadvantage of the prior art,

FIG. 15 shows a turbine blade,

FIG. 16 shows a combustion chamber,

FIG. 17 shows a gas turbine.

FIG. 1 shows a component 1, 120, 130, 138, 155 comprising a substrate 4 and a single outer layer 7.

The substrate 4 is a superalloy on an iron, in particular for components 120, 130, 138, 155 for turbines.

Nickel and / or cobalt base. The outer layer 7 is preferably before ^¬ a corrosion and / or oxidation layer on the basis of an alloy of MCrAlX (Fig. 15). But it can also be ceramic.

The substrate 4 and the layer 7 have at least one film ^¬ cooling hole 28, which has a hot side 22 under the operating conditions a diffuser 13, of the example cylindrical, cuboid or generally symmetrical contour 49 of the lower part 24 of the film cooling hole 28 deviates near a cooling reservoir 31 and increases in cross-section. The film cooling hole 28 thus consists of a lower part 24 and the outer diffuser 13. The diffuser 13 has an outlet opening 58, which is overflowed by a hot gas in the overflow direction 37. The diffuser 13 is formed from an imaginary continuation 12 of the contour 49 to the surface 25 and an additive 14 (FIG. 2), which adjoins one or more side surfaces of the continuation 12. In the cross-sectional view of FIG. 1, the additive 14 preferably has a wedge shape.

In the plane of the outer surface 13 thus comprises the diffuser no rotational symmetry, with a focus of the asym metrical form ^¬ from the gravity center of the symmetric shape of the contour is moved to over-current direction 37, 49th Along the vertical 27 toward the outer surface 25, the cross-sectional area of the film cooling hole 28, on which the vertical 27 is perpendicular, larger, ie the diffuser 13 is fully or preferably partially funnel-shaped ^{ausgebil ¬} det.

According to the invention, the diffuser 13 is arranged for the most part within the single layer 7, that is, when the Diffu ^¬ sor 13 longitudinally with an overall length 19 in the depth of a vertical line 27 of the component 1, which is perpendicular to the outer surface 25 or perpendicular to the overflow 37, extends, the result is a substrate length 16 of the diffuser 13, which represents the proportion of the diffuser 13 in the substrate 4. The length of substrate 16 is significantly smaller formed as the total length of 19. The total coating thickness 26 (here, the layer 7) forms the remaining part of the total length 19 of the diffuser 13. The coating thickness of 26 is Minim ^¬ least 50%, preferably at least 60% or at least 70%, in particular 80% or 90% of the total length 19.

Alternatively, the diffuser 13 may be entirely in the single layer 7 arranged (Fig. 3, layer thickness 26 = total length ^¬ 19). In FIG. 4, two layers are present on the substrate 4.

Again, this is a corrosion and oxidation protection layer 7 is applied on the still an outer ceramic thermal barrier layer ^¬ 10th

As in FIG. 1, there are the lengths 16, 19 of the diffuser 13, wherein the layer thickness 26 again amounts to at least 50%, 60% or in particular 70%, in particular 80% or 90% of the total length 19.

Likewise, the diffuser 13 can be arranged completely in the two layers 7, 10 (FIG. 5).

According to the two layers according to FIGS. 4, 5, this also applies to three or more layers.

As a result of the fact that the diffuser 13 is arranged largely or entirely in the layers 7, 10, there are advantages in the reprocessing of the component 1, for example with regard to laser ablation or removal of material above the lower part 24, which occurs after repainting the component

Component 1 covers the outlet opening 58, namely the fact that the laser or other processing equipment must be adjusted only to the material of the layers 7, 10 and the processing of the other material, namely that of the substrate 4, must be disregarded.

Figure 6 shows a cross section through a component 1 with a

Film cooling hole 28. The substrate 4 has an outer surface 43 on which the at least one layer 7, 10 is applied.

For example, the diffuser 13 is largely (as shown in FIG.

3, 4, 5) in the layer 7, 10, but may also be present entirely in the substrate 4 or for the most part in the substrate 4.

The lower part 24 of the film cooling hole 28 has in longitudinal section, for example, a line of symmetry 46. The symmetry line 46 provides for example, a flow direction from ^¬ 46 for a cooling medium is that flows through the film cooling hole 28th

A contour line 47, which runs parallel to the line of symmetry 46 on the inside of the film-cooling hole 28 or a pro ^¬ jection of the symmetry line 46 to the inside of the lower portion 24 represents the film cooling hole 28 forms an acute angle αl with the outer surface 43, in particular at 30 ° +/- 10%. The film cooling hole 28 is thus inclined in the overflow direction 37.

The edge length a ₂ s (FIG. 8) or the diameter φ ₂ s of the film cooling hole 28 is for example about 0.62 mm or 0.7 mm for rotor blades and about 0.71 mm and 0.8 mm for guide vanes.

The contour line 47, which runs along the contour 49 of the lower part 24 ver preferably parallel to the outflow direction 46 ^¬, has an acute angle α2 with a diffuser line

48, which extends on the inner surface 50 of the additive 14 of the diffuser 13 and which represents a projection of the overflow ^direction 37 onto the inner surface 50 of the additive 14 of the diffuser 13.

The angle α2 is in particular 10 ° +/- 10%. The lower part 24 along the symmetry line 46 has a constant cross-section, in particular an n-number rotational symmetry (square, rectangular, round, oval, ...) has on ^¬ .

The diffuser 13 is formed by the fact that the cross-sectional area of the film cooling hole 28 widened, that is to say it is funnel-shaped in longitudinal section. The addition 14 to the contour

49 does not necessarily extend completely around the outlet opening 58 of the film cooling hole 28, but only partially, in particular by half or less of the circumference of the outlet opening 58.

Preferably, the diffuser 13 is only - seen in the overflow 37 of the hot gas 22 - arranged in the rear region of the opening 58 (Fig. 7). Side lines 38 of the diffuser 13 or the additive 14 extend in plan view, for example, parallel to the overflow direction 37 (FIG. 7).

The total layer thickness of the at least one layer 7, 10 is about 400 μm to 700 μm, in particular 600 μm.

8 shows a further embodiment of the film cooling hole 28 and a plan view of the diffuser 13 in the plane of the outer surface 25 of the layer system or component 1. The additive 14 has, for example, a trapezoidal shape in the plane of the outer surface 25.

In the plane of the surface 25, the addition 14 of the diffuser 13 in the overflow direction 37 has a longitudinal length II, preferably of about 3 mm.

The largest width, ie the diffu- measured sors 13 in the surface, that is perpendicular to the processing Überströmrich ^¬ 37, the largest cross-length I _2, preferably has a size of 2 H- 0.2 mm for blades and a size of 4 H- 0 , 2 mm with guide vanes and is 8 mm at the most.

In the embodiment of Figure 8 the Spread ^¬ begins tion of the diffuser 13 at a widening front edge 62, ie when the appendage 14, and widens in the overflow 37. The overflow direction 37 forms with a side boundary line 38 of the additive 14 in the plane of the outer upper ^¬ surface 25 an acute angle α3, in particular 10 ° +/- 10%.

Preferably, deviating from the contour 49 of the symmetrical for example with respect to two mutually perpendicular axes lower portion 24, the diffuser 13 widened transversely to the overflow 37 each by an angle α3, which is in particular 10 ° +/- 10%, the broadening already at Leading edge 61 (viewed in the overflow direction 37) of the film cooling hole 28 begins and extends to the rear edge ^¬ 64.

Therefore, the diffuser 13 has a trapezoidal cross section in the plane of the surface 25 (Fig. 9). The diffuser 13 is produced by a material removal method, for example, electron irradiation or laser irradiation. Only in this way can a multiplicity of cooling holes be produced accurately and in a reproducible manner.

Figures 10, 11, 12 and 13 illustrate different contours of the film cooling hole 28. The lower portion 24 of the film cooling hole 28 is formed way of example only with cuboid ^¬ here, but can also have a round or oval cross-sectional shape.

In Figure 10, the diffuser 13 is for example only extended in over-flow direction 37, so that the cross-section of from ^¬ opening 58 is larger than the cross section of the lower portion 24 corresponding to the film cooling hole 28 so the film cooling hole according to FIG 2, 6 or 7th

Starting from FIG. 10, FIG. 11 shows a film cooling hole 28 which is still spreading transversely to the overflow direction 37 in the overflow direction 37, that is to say corresponding to FIG.

In FIG. 12, the diffuser 13 is widened, for example, only transversely to the overflow direction 37, so that here too the cross section of the outlet opening 58 is greater than the cross section of the lower part 24. The film cooling hole 28 consists, for example, of a rectangular lower part 24, on which a diffuser 13 in the form of a hexahedron with parallel, trapezoidal side surfaces connects.

In FIG. 13, the diffuser 13 is widened transversely to the overflow direction 37 both in the overflow direction 37 and in both directions. Figures 6, 7, 8, 9, 10, 11 and 13 is that the diffuser is seen in the overflow 37 13 mostly disposed behind the outlet opening 58 respectively to entneh ^¬ men. This means therefore that the diffuser is formed by a saw 13 unsymmet ^¬ generic widening in the overflow 37th A uniform broadening of the cross section of the lower part 24 of the film cooling hole 28 at the level of the outer surface 25 is not intended. In FIG. 6 it can be clearly seen and described that the additive 14 represents the widening of the cross section in the overflow direction 37, whereby the diffuser is formed. This is also shown by the plan view according to FIG. 7 to FIG. 6. In FIG. 8, the broadening of the opening of the cross-section of the film cooling hole in the overflow direction 37 begins from the line 62.

In FIG. 9, the broadening of the diffuser 13 begins as seen at the front edge 61 in the overflow direction 37. A widening of the cross section of the film cooling hole 28 at the level of the outer surface 25 against the overflow direction 37, d. H. in front of the front edge 61 is absent or only to a small extent in comparison to the widening of the cross section in the overflow direction 37.

FIG. 15 shows a perspective view of a moving blade 120 or guide blade 130 of a turbomachine that extends along a longitudinal axis 121.

The turbomachine may be a gas turbine of an aircraft or a power plant for power generation, a steam turbine or a compressor.

The blade 120, 130 has, along the longitudinal axis 121, a fastening area 400, an adjacent blade platform 403 and an airfoil 406, one after another. As a guide vane 130, the vane 130 may have tip at its ^vane 415 a further platform (not Darge ^¬ asserted).

In the mounting region 400, a blade root 183 is formed, which serves for attachment of the blades 120, 130 to a shaft or a disc (not shown). The blade root 183 is, for example, as a hammerhead staltet out ^¬. Other designs as fir tree or Schwäbwschwanzfuß are possible.

The blade 120, 130 has a medium which flows past felblatt 406 at the spectacle ^¬ a leading edge 409 and a ^trailing edge on the 412th

In conventional blades 120, 130, in all regions 400, 403, 406 of the blade 120, 130, for example, ^massive metallic materials, in particular superalloys, are used. Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949; These documents are part of the disclosure regarding the chemical composition of the alloy. The blade 120, 130 can hereby be produced by a casting process, also by directional solidification, by a forging process, by a milling process or combinations thereof.

Workpieces with a monocrystalline structure or structures are used as components for machines which are exposed to high mechanical, thermal and / or chemical stresses during operation.

The production of such monocrystalline workpieces, for example, by directed solidification from the melt. These are casting methods in which the liquid metallic alloy solidifies into a monocrystalline structure, ie a single-crystal workpiece, or directionally. Here, dendritic crystals are aligned along the heat flow and form either a columnar crystalline Grain structure (columnar, ie grains that run the entire length of the workpiece and here, in common usage, are referred to as directionally solidified) or a monocrystalline structure, ie the entire workpiece consists of a (single) crystal. In these methods, you have to transition to globular (polycrystalline) solidification avoided, since non-directional growth inevitably forms transverse and longitudinal grain boundaries ^¬ which the good properties of the directionally solidified or single-crystal component nullify.

The term "directionally solidified structures" generally refers to single crystals that have no grain boundaries or at most small angle grain boundaries, as well as stem crystal structures that have grain boundaries running in the longitudinal direction but no transverse grain boundaries. These second-mentioned crystalline structures are also known as directionally solidified structures. Such methods are known from US Pat. No. 6,024,792 and EP 0 892 090 A1; These documents are part of the Offenba ^¬ tion.

Likewise, the blades 120, 130 may be coatings against corrosion or oxidation (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and is yttrium (Y) and / or silicon and / or at least one element of the rare earths or hafnium (Hf)). Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1, which should be part of this disclosure with regard to the chemical composition of the alloy.

On the MCrAlX still a thermal barrier coating may be present and consists for example of ZrO ₂ , Y ₂ O ₃ -ZrO ₂ , ie it is not, partially or completely stabilized by yttrium ^¬ oxide and / or calcium oxide and / or magnesium oxide. Suitable coating processes, such as electron beam evaporation (EB-PVD), produce stalk-shaped grains in the thermal barrier coating.

Refurbishment means that components 120, 130 may need to be deprotected after use (e.g., by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. Optionally, even cracks in the component 120, 130 are repaired. This is followed by a re-coating of the component 120, 130 and a renewed use of the component 120, 130.

The blade 120, 130 may be hollow or solid. If the blade 120 is to be cooled 130, it is hollow and, if necessary, has film cooling holes 418 ^(indicated by dashed lines) on.

16 shows a combustion chamber 110 of a gas turbine 100. The combustion chamber 110 is designed for example as so-called ^an annular ^combustion chamber, in the circumferential direction in which a plurality of an axis of rotation 102 of burners 107 arranged in a common combustion chamber space 154, the flames 156 generate. For this purpose, the combustion chamber 110 is configured in its entirety as an annular structure, which is positioned around the axis of rotation 102 around.

To achieve a comparatively high efficiency, the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ^° C. to 1600 ^° C. A relatively long service life even with these handy, unfavorable for the materials to operational parameters made ^¬, the combustion chamber wall 153 is provided on its side facing the medium M, Arbeitsme- facing side with a formed from heat shield elements 155. liner.

Each heat shield element 155 made of an alloy is on the working medium side with a particularly heat-resistant protective Layer (MCrAlX layer and / or ceramic coating) equipped or is made of high temperature resistant material (solid ceramic stones).

These protective layers may be similar to the turbine blades, so for example MCrAlX means: M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare earths, or hafnium (Hf). Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1, which should be part of this disclosure with regard to the chemical composition of the alloy.

On the MCrAlX, for example, a ceramic thermal insulation layer may be present and consists for example of ZrO ₂ , Y ₂ O ₃ -ZrO ₂ , ie it is not, partially or fully ^¬ dig stabilized by yttrium and / or calcium oxide and / or magnesium oxide.

By suitable coating methods, e.g. Electron beam evaporation (EB-PVD) produces stalk-shaped grains in the thermal barrier coating.

Reprocessing (Refurbishment) means that ^heat shield elements must be freed 155 after use, where appropriate, protective layers (for example by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. If necessary, cracks in the heat shield element 155 are also repaired. This is followed by a recoating of the heat shield elements 155 and a renewed use of the heat shield elements 155.

Due to the high temperatures inside the combustion chamber 110 may also be provided for the heat shield elements 155 and for their holding elements, a cooling system. The heat shield elements 155 are then, for example, hollow and possibly still have film cooling holes (not shown) which open into the combustion chamber space 154. FIG. 17 shows by way of example a gas turbine 100 in a longitudinal partial section. The gas turbine 100 has an axis by a rotational ^¬ 102 rotatably mounted rotor 103 having a shaft 101, which is also referred to as the turbine rotor. Along the rotor 103 follow one another an intake housing 104, a compressor 105, for example, a toroidal combustion chamber 110, in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th

The annular combustion chamber 110 communicates with an annular annular hot gas channel 111, for example. There, for example, four turbine stages 112 connected in series form the turbine 108.

Each turbine stage 112 is formed, for example, from two blade ^rings . As seen in the direction of flow of a working medium 113, in the hot gas channel 111 of a row of guide vanes 115, a series 125 formed of rotor blades 120 follows.

The guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example.

Coupled to the rotor 103 is a generator or work machine (not shown).

During operation of the gas turbine 100 104 air 135 is sucked by the compressor 105 through the intake housing and ver ^¬ seals. The be at the turbine end of the compressor 105 ^¬ compressed air provided to the burners will lead 107 ge ^¬ where it is mixed with a fuel. The mixture is then burned to form the working medium 113 in the combustion chamber 110. From there, the working medium flows

113 along the hot gas channel 111 past the guide vanes 130 and the blades 120. On the blades 120, the working medium 113 relaxes in a pulse-transmitting manner, so that the blades 120 drive the rotor 103 and drive the machine coupled to it.

The components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100. The guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the flow direction of the working medium 113, are subjected to the highest thermal stress in addition to the heat shield elements lining the annular combustion chamber 110.

To withstand the prevailing temperatures, they can be cooled by means of a coolant. Likewise, substrates of the components may have a directional structure, i. they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).

As a material for the components, in particular for the ^turbine blade or vane 120, 130 and components of the combustion chamber 110, for example, iron, nickel or cobalt-based alloys used Superle-. Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949; These documents are part of the disclosure regarding the chemical composition of the alloys.

Also, the blades 120, 130 may be anti-corrosion coatings (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and is yttrium (Y) and / or silicon and / or at least one element of the rare earths or hafnium). Such alloys are known from EP 0 486 489 B1, EP

0 786 017 Bl, EP 0 412 397 B1 or EP 1 306 454 A1, which are to be part of this disclosure with regard to the chemical composition.

On the MCrAlX may still be present a thermal barrier coating, and consists for example of ZrO ₂ , Y ₂ O ₃ -ZrO ₂ , ie it is not, partially or completely stabilized by Ytt ^¬ riumoxid and / or calcium oxide and / or magnesium oxide. Suitable coating processes, such as electron beam evaporation (EB-PVD), produce stalk-shaped grains in the thermal barrier coating.

The guide vane 130 has an inner housing 138 of the turbine 108 facing guide vane root (not provide Darge ^¬ here) and a side opposite the guide-blade root vane root. The vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.

Claims

claims

1. component having at least one film cooling hole (28), the component (1) consisting of a substrate (4) and at least one layer (7, 10), the film cooling hole (28) having a diffuser (13) in the outer region,

characterized,

that the entire diffuser (13) mostly in the at ^¬ least one layer (7, 10) is arranged such that the total coating thickness (26) at least 60%, especially 70%, along a perpendicular (27) to the outer surface (25 ) of the at least one layer (7, 10) measured total length (19) of the diffuser (13).

2. Component according to claim 1, characterized in that

the coating thickness (26) is at least 80%, in particular 90% of the total length (19) of the diffuser (13).

3. Component according to claim 1, characterized in that

the coating thickness (26) is equal to the total length (19) of the diffuser (13).

4. Component according to claim 1, 2 or 3, characterized

that the substrate (4) having an outer surface (43), and that the film cooling hole (28) at a 0 ° various ^¬ which acute angle (αl) to the outer surface (43), in particular of 30 ° - 45 °, in the at least one layer (7, 10) extends.

5. Component according to one or more of the preceding claims, characterized

in that a hot gas flows over the film cooling hole (28) in the overflow direction (37), that a medium flows through the film cooling hole (28) in the outflow direction (46), that the film cooling hole (28) has a lower part (24), that the diffuser ( 13) as part of the film cooling hole (28) adjoins the lower part (24) and in the outflow (46) has a perpendicular to the outflow direction (46) widening cross section, the cross section of the diffuser (13) in particular only in the overflow ( 37) widened.

6. Component according to one or more of the preceding claims, characterized

that a hot gas, the film cooling hole (28) in the overflow direction

(37) flows over a medium, the film cooling hole (28) in the outflow direction

(46) flows through the film cooling hole (28) has a lower part (24) that the diffuser (13) as part of the film cooling hole (28) adjoins the lower part (24) that a contour line (47) along the contour (49) of the lower part (24) parallel to the outflow direction (46) runs that a diffuser line (48) on the inside of the diffuser (13) extends, (48) a projection of the overflow (37 ) on the

Inner surface of an additive (14) of the diffuser (13) is, and that the diffuser line (48) has an acute angle (α2), in particular of 10 °, with the contour line (47).

7. Component according to one or more of the preceding claims, characterized

in that a hot gas flows over the film cooling hole (28) in the overflow direction (37), that the film cooling hole (28) has a lower part (24), that the diffuser (13) as part of the film cooling hole (28) contacts the lower part (24) connects and that the diffuser (13) in the plane of the outer surface (25) of the layer (7, 10) in the overflow (37) by an acute angle (α3) to the overflow (37), in particular by 10 °, transverse to Overflow (37) widened.

8. Component according to one or more of the preceding claims, characterized

in that a hot gas flows over the film cooling hole (28) in the overflow direction (37), that a medium flows through the film cooling hole (28) in the outflow direction (46), that the film cooling hole (28) has a lower part (24), that the diffuser (13) as part of the film cooling hole (28) adjoins the lower part (24) and in the outflow (46) has a perpendicular to the outflow direction (46) widening cross-section, the surface of the diffuser (13) in the overflow (37) seen at height the surface (25) is arranged largely behind the film cooling hole (28).

9. Component according to claim 7, characterized

the outlet opening (58) of the film cooling hole (28) has a front edge (61) and a rear edge (64) in the overflow direction (37), and in that the diffuser (13) is in the plane of the outlet ^opening from the front edge (61 Widened starting, so that the diffuser (13) in the plane of the outer surface (25) is trapezoidal.

10. Component according to claim 7, characterized

in that the diffuser (13) consists of a continuation of the contour (49) of the lower part (24) and an attachment (14) and that only the additive (14) of the diffuser (13) widens towards the outer surface (25) in that it (14) is trapezoidal in the plane of the outer surface (25).

11. Component according to claim 9, characterized

that between the overflow direction (37) and a lateral boundary line (38) of the additive (14) of the diffuser (13) in the plane of the surface (25) is given an acute angle of (α3), in particular of 10 °.

12. Component according to claim 5 or 7, characterized

that the diffuser (13) has in the plane of the outer surface (25) in the overflow (37) has a longitudinal length (I ₁₎ on ^¬, which is in particular 3 mm, and in that the broadest transverse length (I ₂₎ perpendicular to the longitudinal length (li) at most 10mm, in particular 2 to 4mm.

13. Component according to claim 1, 2 or 3, characterized in that

an outer layer (10) is applied to an intermediate layer (7).

14. Component according to claim 12, characterized

in that the intermediate layer (7) consists of the alloy of the MCrAlX type and in that the outer layer (10) is in particular a ceramic one

Represents thermal insulation layer.

15. Component according to claim 1, 12 or 13, characterized in that

the component (1) is a component of a steam or gas turbine (100), in particular a turbine blade (120, 130), a heat shield element (155).